Jet propeller engine



March 29, 1949. v

Filed Nov 12 1946 Mardi 29, 1949.

H. E. EMIGH 2,465,856

JET PROPELLER ENGINE P11901 Nov. 12, 194e 2 sheets-sheet 2 INVEN TOR.Harold E. Emigh.

HTTORNEY.

Patented Mar. 29, 1949 OFI-*ica JET PRoPELLER ENGINE Hernia E. Emigh,Long neuen, oeuf.v Application November 12, 1946,` sei-iai No. 709,368 1claim. (ci. 17o-1135.4)

This invention relates to a jet propeller engine wherein the fuel is fedinto the blades of the propeller, is there compressed by centrifugalforce, and moved into an explosion chamber where the gases are ignitedand exhaust in the trailing edge of the blades.

An object of my invention is to provide a novel jet propeller enginewhich is light in weight, is compact and is relatively simple inconstruction.

Another object of my invention is to provide a novel jet propellerengine wherein the power of the burning gases is exerted atorapproxlmately at the tip of the blades, thus providing a long torquearm and giving the maximum amount of power possible.

Another object of my invention is to provide a novel engine of thecharacter stated wherein the incoming fuel is rst compressed in asupercharger unit, is then further compressed by centrifugal forcewithin the blades, and is then moved into a burning chamber at the tipof the blade, this chamber being open at the forward or leading edge toprovide a blast to assist in scavenging the burner chamber.

A feature of my invention resides in the adaptability of my engineconstruction to both a fixed pitch propeller or a variable pitchpropeller.

Another feature of my invention is to provide a novel means of drivingthe supercharger. this means being simple and compact.

Other objects, advantages and features of invention may appear from theaccompanying drawing, the subjoined detailed description and theappended claim.

In the drawing:

Figure 1 is a fragmentary longitudinal sectional view of my engine, andin which thel section lineI is offset at the center of the propeller tobisect both of the offset blades and sockets.

Figure 2 is a fragmentary transverse sectionalr view of one of theblades.

Figure 3 is a front elevation of the hub section.

Figure 4 is a rear elevation with parts broken away of the gear train.

Referring more particularly to the drawing, my jet propeller engine Iconsists of a hub 2 which is formed in two parts 3 and 4. 'I'he hubhalves J and 4 are bolted together by means of a plurality of bolts 5.all of which is usual and well known in propeller construction. Aplurality of blades 5 extend radially from the hub 2. and these bladesare hollow from the base to the tip so as to act as a conduit for thefuel as will be subsequently described. The blades 5 are held In the hub2 by means of the ring 5, all of which is usual and well known in theart.

It is evident that the blades 5 may be either fixed in pitch or avariable pitch construction nay be employed, if desired. At the outerend if each of the blades 5, I provide a burner cham- 2 ber 'I whichfairs into signed that little or no resistance or air interference isencountered because of this chamber. The chamber is opened at theleading edge as shown at 8 and at the rear of the trailing edge of theblade a'Venturi port 9 is provided. The purpose of the opening 8, is tointroduce blast air from the forward motion of the plane, and rotationof the propeller; into the chamber l, which increases the compression ofthe gases in chamber'l, above the pressures generated by thesupercharger. i

A second intake Venturi port In is provided between the hollow blade 5and the chamber 1. The purpose of this Venturi intake port is to furtherincrease the pressures of the fuel as the fuel passes into the burningchamber 1. An

igniter Il is mounted in the chamber 'I and aI wire conduit I2 extendsto the igniter from a contact ring I 3 on the hub2.

A hollow shaft I 4 is either keyed to the hub 2 or may be an integralpart of this hub if desired. 'I'his hollow shaft extends rearwardly andis Jom'nalled in the accessory case I5 by suitable bearings I8, I1. Aring gear I8 is fixedly attached tothe shaft I4 and this gear mesheswith the spur gears I9, of which there may be two 4or more. to the shaftof the gears 20, or directly to these gears, if desired. Thus, the gearsI9, 20 rotate together. 'I'he gears 2n in' turn mesh with a gear 2|,this latter gear being secured to the supercharger shaft 22. 4Asupercharger impeller 23 is xed to the shaft 22, and is positionedwithin the hub 2. An opening 24 is provided in the front of the half 3of the hub so that blast air can pass into the impeller 23. 'I'he bladesof thev impeller are suitably curved within the area of the opening 24so as to draw air horizontally into the supercharger, and this air isthen compacted, and is thrown radially into the hollow blades 5. 'I'heblades 5 are preferably arranged in the hub 3 so that the center linesof the blades are substantially tangent to the perifery of the impeller23.

It will be evident from the foregoing description that when thepropeller is rotating the supercharger 23 will also be rotated, and ingeared relation to the rotation of the propeller blades.

Fuel is introduced to the engine through the pipe 25 and the fitting 26,and thence into the bore 21 in the shaft 22 and thence into the impeller23, Where the fuel is mixed with the incoming air passing through theopening 24, and is thencarried radially outward into the blades 5 andthence into the burner chamber 1 where the charge is burned and isthrough the port 8 causing a rotative force to be imparted to thepropeller blades, and thus driving the aircraft. The accessory housingI5 the blade s anais so ae- The gears I 9 are fixedly attached thenjetted outwardly is provided with a cover 2l and various accessories(such as the starter 29) may be mounted on this cover and driven by theshafts on which the gears 20 are mounted. The accessory housing Il isalso the oil sump, the oil being distributed to the necessary parts ofthe engine by the' gear train. An over running bearing 3l is providedbetween the starter gear Il and the shaft I4, thus providing a meanswhereby the supercharger can be rotated at high speed for startingpurposes.

Having described my invention, I claim:

A jet propeller engine comprising a hub, hollow blades projecting fromsaid hub, a burner chamber adjacent the tip` of the blades, said chamberhaving an opening at. the leading edge of the blade, and an exhaustopening at the trailing edge of the blade, a. supercharger mounted insaid hub, said hub having an air intake opening in the front thereof,extending into the supercharger, and fuel intake means extending intothesupercharger, said chamber having an intake port communicating withthe hollow blade 4 and positioned within said blade. said intake portbeing Venturi shaped.

HAROLD E. EMIGH.

REFERENCES CITED The following references are of record in the ille ofthis patent:

UNITED STATES PATENTS Number Name l Date 1,569,607 Beck Jan. l2, 19261,923,054 Holmes et al Aug. 15, 1933 2,142,601 Bleecker Jan. 3, 19392,330,056 Howard Sept. 21, 1943 2,371,678 Gerhardt Mal'. 20, 19452,397,357 Kundig Mar. 26, 1946 FOREIGN PATENTS Number Country Date227,151 Great Britain Jan. 12, 1925 366,450 Great Britain 1930 423,590France Apr. 24, 1910 648,107 France Aug. 7, 1928

